Results
96-17-14: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and B4 series airplanes, that currently requires repetitive visual inspections to detect cracks in the forward intermediate section skin at frame 30A where it joins stringer 30, and repair, if necessary. This amendment adds a requirement for eddy current inspection(s) to detect cracks of the outer skin of the fuselage; accomplishment of this inspection terminates the repetitive visual inspections. This amendment also requires repair of any cracked area and modification of the structure at certain frames. This amendment is prompted by in-service experience which has identified fatigue cracks in this area. The actions specified by this AD are intended to prevent fatigue cracking, which could result in rapid decompression of the airplane.
2018-04-11: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. Model AB139 and Model AW139 helicopters. This AD requires inspecting the thickness of the tail gearbox (TGB) central housing (housing). This AD was prompted by reports that the housing thickness does not conform to its type design. The actions of this AD are intended to detect and correct an unsafe condition on these products.
99-05-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that requires revising the maintenance program to require verification that a certain shipping container and shipping sleeve assembly were used in shipping the ram air turbine (RAT) deployment actuator. This amendment also requires inspection of the identification plate on the RAT deployment actuator to determine the actuator serial numbers or a records check to determine such information; and repair or replacement of certain RAT deployment actuators, if necessary. This amendment is prompted by reports of certain RAT actuators that failed to deploy upon command due to interference in the actuator locking mechanism caused by damage incurred during shipping of the actuators. Failure of the RAT to deploy, specifically during a dual engine failure, would result in loss of hydraulic power and would adversely affect the continued safe flight and landing of the airplane.
99-05-12: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-100, -200, -300, -400, and -500 series airplanes. This action requires removal of the float switch and wiring and inspection of the float switch wiring in the center fuel tank to detect discrepancies, and either reinstallation of existing float switch and wiring, or replacement of the float switch and wiring with a new float switch and wiring. This action also requires installation of Teflon sleeving over the wiring of the float switch. In lieu of the above mentioned requirements, this AD requires deactivation of the float switch, accomplishment of specific fueling procedures, and installation of Caution signs. This amendment is prompted by a report indicating that chafing of the direct current (DC) powered float switch wiring insulation in the center fuel tank has occurred on several airplanes. The actions specified in this AD are intended to detect and correct suchchafing and the resultant arcing from the wiring to the in-tank conduit, which could present an ignition source inside the fuel tank and consequent fire/explosion.
99-05-08: This amendment adopts a new airworthiness directive (AD) that is applicable to McDonnell Douglas Helicopter Systems (MDHS) Model MD-900 helicopters. This action requires establishing or reducing certain life limits, applying serial numbers (S/N's), determining hours time-in-service (TIS), and creating component history cards or equivalent records for various parts. This amendment is prompted by analysis that indicates a need for establishing or reducing life limits to avoid fatigue failure of certain parts. The actions specified by this AD are intended to apply appropriate life limits to various parts.
93-01-26: 93-01-26 DE HAVILLAND, INC.: Amendment 39-8480. Docket 92-NM-99-AD. Supersedes AD 91-19-04, Amendment 39-8031 which superseded AD 91-12-51, Amendment 39-7076. Applicability: Model DHC-8-300 series airplanes; serial numbers 202, 210, 216, 221, 224, 230, 232, 234, 236, 238, 240, 242, 244, 246, 248, 250, 252, 254, 256, 257, 259, 261, 262, 264, 266, 267, 269, 271, 272, 274, 276, 278, 279, 281, 283, 284, 286, 288, and 307; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent the accumulation of fuel vapors in the dry bay area, presenting a potential risk of an in-flight explosion in the event of a lightning strike, accomplish the following: (a) For those airplanes listed in de Havilland Alert Service Bulletin S.B. A8-28-16, dated May 30, 1991, accomplish the following: (1) Within 24 hours after August 26, 1991 (the effective date of AD 91-12- 51, Amendment 39-7076), and thereafter at intervals not to exceed 300 hours time-in-service or 30 days, whichever occurs first, perform an external visual inspection of the wing dry bay drains for blockage in accordance with the service bulletin. If drain blockage is found, prior to further flight, repair in accordance with paragraph B.1. of the Accomplishment Instructions of the service bulletin. (2) Within 24 hours after August 26, 1991, and thereafter at daily intervals, perform an external visual inspection of the wing dry bay drains to detect evidence of fuel leaks in accordance with the service bulletin. (3) Within 7 days after August 26, 1991, unless accomplished within the previous 14 days; or prior to further flight if evidence of fuel leaks is detected at the wing dry bay drains as a result of the inspection required by paragraph (a)(2) of this AD; perform an internal visual inspection of the wing dry bay in accordance with the service bulletin. (i) If no leakage is found as a result of the inspection required by paragraph (a)(3) of this AD, repeat the internal visual inspection of the wing dry bay required by paragraph (a)(3) of this AD at intervals not to exceed 14 days. (ii) If the leakage is within the limits specified in the service bulletin, within 14 days, perform the local re-sealing repair procedure described in paragraph C.7. of the Accomplishment Instructions of the service bulletin. The airplane may be returned to service within this 14-day period, subject to the following conditions: (A) Perform the internal visual inspection of the wing dry bay required by paragraph (a)(3) of this AD at intervals not to exceed 7 days to ensure that the leakage remains within the specified limit; and (B) Prior to further flight, incorporate the following into the Limitations Section of the Airplane Flight Manual (AFM), which may be accomplished by including a copy of this airworthiness directive in the AFM: "Flight is prohibited in areas where lightning or thunderstorms are observed or reported within 5 nautical miles of the flight path, or when the existing weather conditions may reasonably be expected to result in a lightning strike." (iii) If leakage exceeds the limit specified in the service bulletin, prior to further flight, repair in accordance with paragraph C.7. of the Accomplishment Instructions of the service bulletin. (iv) Application of a fuel vapor barrier coating in accordance with paragraph D. of the Accomplishment Instructions of the service bulletin constitutes terminating action only for the repetitive internal visual inspections required by paragraph (a)(3)(i) of this AD. (b) For those airplanes listed in de Havilland Alert Service Bulletin S.B. A8-28-16, Revision 'B', dated June 24, 1991, that are not subject to paragraph (a) of this AD, accomplish the following: (1) Within 24 hours after September 26, 1991 (the effective date of AD 91- 19-04, Amendment 39-8031), and thereafter at intervals not to exceed 300hours time-in-service or 30 days, whichever occurs first, perform an external visual inspection of the wing dry bay drains for blockage in accordance with the service bulletin. If drain blockage is found, prior to further flight, repair in accordance with paragraph B.1. of the Accomplishment Instructions of the service bulletin. (2) Within 24 hours after September 26, 1991, and thereafter at daily intervals, perform an external visual inspection of the wing dry bay drains to detect evidence of fuel leaks in accordance with the service bulletin. (3) Within 7 days after September 26, 1991, unless accomplished within the previous 14 days; or prior to further flight if evidence of fuel leaks is detected at the wing dry bay drains as a result of the inspection required by paragraph (b)(2) of this AD; perform an internal visual inspection of the wing dry bay in accordance with the service bulletin. (i) If no leakage is found as a result of the inspection required by paragraph (b)(3) of this AD, repeat the internal visual inspection of the wing dry bay required by paragraph (b)(3) of this AD at intervals not to exceed 14 days. (ii) If the leakage is within the limits specified in the service bulletin, within 14 days, perform the local re-sealing repair procedure described in paragraph C.7. of the Accomplishment Instructions of the service bulletin. The airplane may be returned to service within this 14-day period, subject to the following conditions: (A) Perform the internal visual inspection of the wing dry bay required by paragraph (b)(3) of this AD at intervals not to exceed 7 days to ensure that the leakage remains within the specified limit; and (B) Prior to further flight, incorporate the following into the Limitations Section of the Airplane Flight Manual (AFM), which may be accomplished by including a copy of this airworthiness directive in the AFM: "Flight is prohibited in areas where lightning or thunderstorms are observed or reported within 5 nautical miles of the flight path, or when the existing weather conditions may reasonably be expected to result in a lightning strike." (iii) If leakage exceeds the limit specified in the service bulletin, prior to further flight, repair in accordance with paragraph C.7. of the Accomplishment Instructions of the service bulletin. (iv) Application of a fuel vapor barrier coating in accordance with paragraph D. of the Accomplishment Instructions of the service bulletin constitutes terminating action only for the repetitive internal visual inspections required by paragraph (b)(3)(i) of this AD. (c) For airplane serial numbers 279, 281, 283, 284, 286, 288, and 307, accomplish the following in accordance with de Havilland Alert Service Bulletin S.B. A8-28-16, Revision 'C', dated January 31, 1992: (1) Within 7 days after the effective date of this AD, and thereafter at intervals not to exceed 300 hours time-in-service or 30 days, whichever occurs first, perform an external visual inspection of the wing dry bay drains for blockage in accordance with the service bulletin. If drain blockage is found, prior to further flight, repair in accordance with paragraph B.1. of the Accomplishment Instructions of the service bulletin. (2) Within 7 days after the effective date of this AD, and thereafter at daily intervals, perform an external visual inspection of the wing dry bay drains to detect evidence of fuel leaks in accordance with the service bulletin. (3) Within 7 days after the effective date of this AD, unless accomplished within the previous 14 days; or prior to further flight if evidence of fuel leaks is detected at the wing dry bay drains as a result of the inspection required by paragraph (c)(2) of this AD; perform an internal visual inspection of the wing dry bay in accordance with the service bulletin. (i) If no leakage is found as a result of the inspection required by paragraph (c)(3) of this AD, repeat the internal visual inspection of the wing dry bay required by paragraph (c)(3) of this AD at intervals not to exceed 14 days. (ii) If the leakage is within the limits specified in the service bulletin, within 14 days, perform the local re-sealing repair procedure described in paragraph C.7. of the Accomplishment Instructions of the service bulletin. The airplane may be returned to service within this 14-day period, subject to the following conditions: (A) Perform the internal visual inspection of the wing dry bay required by paragraph (c)(3) of this AD at intervals not to exceed 7 days to ensure that the leakage remains within the specified limit; and (B) Prior to further flight, incorporate the following into the Limitations Section of the Airplane Flight Manual (AFM), which may be accomplished by including a copy of this airworthiness directive in the AFM: "Flight is prohibited in areas where lightning or thunderstorms are observed or reported within 5 nautical miles of the flight path, or when the existing weather conditions may reasonably be expected to result in a lightning strike." (iii) If leakage exceeds the limit specified in the service bulletin, prior to further flight, repair in accordance with paragraph C.7. of the Accomplishment Instructions of the service bulletin. (iv) Application of a fuel vapor barrier coating in accordance with paragraph D. of the Accomplishment Instructions of the service bulletin constitutes terminating action only for the repetitive internal visual inspections required by paragraph (c)(3)(i) of this AD. (d) Within 6 months after the effective date of this AD, accomplish Modification No. 8/1776 in accordance with de Havilland Service Bulletin S.B. 8-57-20, Revision A, dated January 31, 1992. Accomplishment of this modification constitutes terminating action for the requirements of this AD. (e) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, New York Aircraft Certification Office (ACO), ANE-170, FAA, Engine and Propeller Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO. (f) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (g) Certain inspections, repairs, and modification shall be done in accordance with de Havilland Alert Service Bulletin S.B. A8-28-16, dated May 30, 1991; de Havilland Alert Service Bulletin S.B. A8-28-16, Revision 'C', dated January 31, 1992; and de Havilland Service Bulletin S.B. 8-57-20, Revision 'A', dated January 31, 1992; as indicated. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Certain other inspections, repairs, and modifications shall be done in accordance with de Havilland Alert Service Bulletin S.B. A8-28-16, Revision 'B', dated June 24, 1991. Incorporation by reference of de Havilland Alert Service Bulletin S.B. A8-28-16, Revision 'B', dated June 24, 1991, was approved previously by the Director of the Federal Register as of September 26, 1991 (56 FR 46228, September 11, 1991). Copies may be obtained from de Havilland, Inc., Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, New York Aircraft Certification Office, 181 South Franklin Avenue, Valley Stream, New York; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington,DC. (h) This amendment becomes effective on March 10, 1993.
2003-04-17: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and MD-11F airplanes, that requires an inspection to detect damage of the wiring/bundles routed to the wire support bar of the circuit breaker panel and to the circuit breakers, and an inspection of the wiring/bundles for correct routing. This amendment also requires installation of protective sleeving, spacers, and sta-straps; and corrective/follow-on actions, if necessary. The actions specified by this AD are necessary to prevent chafing and consequent arcing or loss of electrical power to associated avionics buses in the upper avionics circuit breaker panel of the main observer's station, which could result in smoke and/or fire in the cockpit. This action is intended to address the identified unsafe condition.
73-23-07: 73-23-07 CESSNA: Amdt. 39-1744. Applies to Model 150 (S/Ns 15074635 thru 15074799); Model A150 (S/Ns A1500415 thru 1500427); Model 172 (S/Ns 17261664 thru 17261808); Model 180 (S/Ns 18052335 thru 18052349); Model 182 (S/Ns 18261960 thru 18262105) and Model 185 (S/Ns 18502199 thru 18502238) airplanes. Compliance: Required as indicted, unless already accomplished. To prevent defective spar attachment fitting from remaining in service, within the next 50 hours' time in service after the effective date of this AD, replace P/N 0523306 wing attach fittings with Cessna Service Kit SK 150-45A, dated July 27, 1973, referred to in Cessna Service Letter SE73-20, dated August 17, 1973, or later FAA-approved revisions, or with any other airworthy part approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective November 19, 1973.
2003-08-08: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes, that currently requires, among other actions, a one-time inspection to detect discrepancies at certain areas around the entry light connector of the sliding ceiling panel above the forward passenger doors; repair, if necessary; and installation or modification of a flapper door ramp deflector on the forward entry drop ceiling structure. That AD also currently requires an inspection of the wire assembly support installation above the entry door (L1) sliding panel for chafing, and repair, if necessary. This amendment requires the existing requirements and requires replacing the wire support bracket with new support clip assemblies. The actions specified by this AD are intended to prevent chafing of electrical wire assemblies above the forward passenger doors and above the entry door (L1) sliding panel of the forward drop ceiling on the passenger compartment, which could result in electrical arcing, and consequent electrical fire in the passenger compartment. This action is intended to address the identified unsafe condition.
99-05-05: This amendment adopts a new airworthiness directive (AD), applicable to International Aero Engines AG (IAE) V2500-A1 series turbofan engines, that requires initial and repetitive inspections of certain High Pressure Turbine (HPT) stage 1 and stage 2 disks utilizing an improved ultrasonic method when the disks are exposed during a normal shop visit, and if a subsurface anomaly is found, removal from service and replacement with a serviceable part. This amendment is prompted by the results of a stage 1 HPT disk fracture investigation which has identified a population of HPT stage 1 and 2 disks that may have subsurface anomalies formed as a result of the processes used to manufacture the material. The actions specified by this AD are intended to prevent HPT disk fracture, which could result in an uncontained engine failure, and damage to the airplane.
99-04-19: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 777 series airplanes. This action requires repetitive detailed visual inspections to detect cracking of the cove skin on the outboard leading edge slats; a slat adjustment check; and corrective actions, if necessary. This amendment is prompted by reports of fatigue cracking and/or missing pieces of the cove skin on the outboard leading edge slats. The actions specified in this AD are intended to detect and correct such discrepancies, which could result in skin separation or structural damage to the leading edge slats, and consequent reduced controllability of the airplane.
2012-11-14: We are adopting a new airworthiness directive (AD) for all Pratt & Whitney Canada (P&WC) PW118, PW118A, PW118B, PW119B, PW119C, PW120, PW120A, PW121, PW121A, PW123, PW123B, PW123C, PW123D, PW123E, PW123AF, PW124B, PW125B, PW126A, PW127, PW127E, PW127F, PW127G, and PW127M turboprop engines. This AD requires initial and repetitive inspections of certain serial numbers (S/Ns) of propeller shafts for cracks and removal from service if found cracked. This AD was prompted by reports of two propeller shafts found cracked at time of inspection during maintenance. We are issuing this AD to detect propeller shaft cracks, which could cause failure of the shaft, propeller release, and loss of control of the airplane.
74-16-04: 74-16-04 BEECH: Amendment 39-1908. Applies to Models 65-B80 (Serial Numbers LD-452 through LD-468), C90 (Serial Numbers LJ-552 through LJ-588) and E90 (Serial Numbers LW-1 through LW-56) airplanes. \n\n\tCompliance: Required as indicated, unless already accomplished. \n\n\tTo prevent restricted elevator travel, within the next 100 hours' time in service after the effective date of this AD, accomplish the following: \n\n\tInstall a MS20365-428 self-locking nut on the threaded portion of each of the four elevator control stop bolts in accordance with the attached sketch and Part I of Beechcraft Service Instruction 0618-152 or subsequent revisions or by any equivalent method of compliance approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. \n\n\tThis amendment becomes effective August 6, 1974.
99-04-23: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737 series airplanes, that requires repetitive ultrasonic inspections to detect broken bolts that attach the terminal support fittings to the upper part of the Body Station 1088 bulkhead, and corrective actions, if necessary. This amendment also requires eventual replacement of the existing bolts with new, improved bolts, which, when accomplished, terminates the repetitive inspection requirements of this AD. This amendment is prompted by reports that bolts that attach the terminal support fittings to the upper part of the bulkhead were found broken. The actions specified by this AD are intended to prevent such broken bolts, which could result in reduced structural integrity of the vertical fin installation and possible loss of the vertical fin.
2012-13-07: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD requires inspecting parts or doing a records review to determine if certain trailing edge flap carriages are installed, doing repetitive inspections for corrosion, and flaking or missing thermal coating on suspect carriage spindles, and related investigative and corrective actions, if necessary; this AD also provides optional terminating action for the repetitive inspections. This AD was prompted by reports of corrosion found on carriage that are located on the outboard flaps. We are issuing this AD to detect and correct corrosion of the carriage spindle, which could result in a fracture; fracture of both the inboard and outboard carriage spindles, at the forward ends through the large diameters, on a single flap assembly, could adversely affect the continued safe flight and landing of the airplane.
2009-07-01 R1: We are rescinding an airworthiness directive (AD) for RRD BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 turbofan engines. The existing AD resulted from the need to reduce the published life limits of high-pressure (HP) turbine stage 1 discs, part numbers (P/Ns) BRH20130 and BRH20131, and HP turbine stage 2 discs, P/Ns BRH19423 and BRH19427. We are rescinding the existing AD because RRD has revised the approved published life limits of these parts to the same or higher limits as originally certified.
68-08-03: 68-08-03 FAIRCHILD-HILLER: Amdt. 39-583. Applies to all F-27 type aircraft Serial Nos. 1 to 95 inclusive incorporating a combustion heater system. Compliance required as indicated unless already accomplished, or unless installed heaters are rendered electrically inoperative and heater controls are placarded to prohibit operation prior to compliance with this AD. To preclude the possibility of residual fuel fire in the heater outer air passage due to lack of adequate drainage, accomplish the following: (a) Within the next 400 operational heater hours after the effective date of this AD, incorporate a heater outer pass drain installation in accordance with Fairchild Service Bulletin No. 21-68 Revision No. 1 dated November 10, 1964, or later FAA-approved revision, or an equivalent modification approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (b) Upon the effective date of this AD heater operational hours will be logged until such time as the AD has been complied with. This amendment effective May 19, 1968.
99-04-03: This amendment adopts a new airworthiness directive (AD), applicable to International Aero Engines AG (IAE) V2500-A5/-D5 series turbofan engines, that requires the removal from service of certain high pressure compressor (HPC) stage 9-12 drums prior to reaching the new reduced cyclic life limits, and replacement with serviceable parts. This amendment is prompted by the reduction of the life limit for certain IAE V2500 HPC stage 9-12 drums due to higher stresses in this part than originally predicted. The actions specified by this AD are intended to prevent high pressure compressor (HPC) stage 9-12 drum failure, which could result in an uncontained engine failure and damage to the aircraft.
99-04-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Pratt & Whitney (PW) JT9D series turbofan engines, that requires a fluorescent penetrant inspection (FPI) of the rear skirt of the diffuser case for cracks, and, if necessary, blending down to minimum wall thickness to remove cracks and subsequent FPI to determine if cracks have been removed, polishing, and shotpeening. If the cracks are shown by subsequent FPI not to have been removed, this AD requires removing the diffuser case from service and replace with a serviceable part. This amendment is prompted by a report of a diffuser case rupture during takeoff roll that resulted in damage to the aircraft. The actions specified by this AD are intended to prevent diffuser case rupture due to cracks, which can result in an uncontained engine failure and damage to the aircraft. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the FederalRegister as of April 12, 1999.
2012-11-09: We are superseding an existing airworthiness directive (AD) for certain transport category airplanes. That AD currently requires either activating all chemical oxygen generators in the lavatories until the generator oxygen supply is expended, or removing the oxygen generator(s); and, for each chemical oxygen generator, after the generator is expended (or removed), removing or restowing the oxygen masks and closing the mask dispenser door. This new AD requires installing a supplemental oxygen system in affected lavatories, which terminates the requirements of the existing AD. This AD was prompted by reports that the current design of the oxygen generators presents a hazard that could jeopardize flight safety. We are issuing this AD to eliminate a hazard that could jeopardize flight safety, and to ensure that all lavatories have a supplemental oxygen supply.
67-32-05: 67-32-05 VICKERS: Amdt. 39-524 Part 39 Federal Register December 12, 1967. Applies to Viscount Models 744, 745D and 810 Series Airplanes. Compliance required as indicated. To prevent failure of the hydraulic flexible hoses installed in the nose wheel steering system, accomplish the following: (a) Replace hydraulic system flexible hoses P/N 70126-163, 70826-13, and 7246-1, located on the top of the nose oleo in the nose steering system, with 6,500 or more hours' time in service or which have been installed for 4 1/2 or more years on the effective date of this AD with new hoses of the same part number within the next 8 months or 1,500 hours' time in service, whichever occurs sooner after the effective date of this AD, and thereafter at intervals not to exceed 5 years or 8,000 hours' time in service, whichever occurs sooner from the last replacement. (b) Replace hydraulic system flexible hoses P/N 70126-163, 70826-13, and 72426-1, located on the top of the nose oleo leg in the nose steering system, with less than 6,500 hours' time in service and which have been installed for less than 4 1/2 years on the effective date of this AD with new hoses of the same part number before the accumulation of 5 years or 8,000 hours' time in service, whichever occurs sooner after the effective date of this AD, and thereafter at intervals not to exceed 5 years or 8,000 hours' time in service, whichever occurs sooner from the last replacement. (British Aircraft Corporation Preliminary Technical Leaflets (PTLS) Nos. 268 (700 Series) and 131 (800 Series), Issue 1, dated June 22, 1967, pertain to this subject.) This amendment effective January 11, 1968.
99-04-08: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Models 1900, 1900C, and 1900D airplanes. This AD requires inspecting the main landing gear hydraulic actuators to determine whether a certain Frisby Aerospace actuator is installed, and reworking or replacing any of these Frisby Aerospace actuators. This AD is the result of reports of fatigue cracks in the end cap of main landing gear hydraulic actuators manufactured by Frisby Aerospace and installed on the affected airplanes. The actions specified by this AD are intended to prevent the main landing gear from failing to lock down due to the hydraulic actuator cracking and separating, which could result in loss of control of the airplane during landing, taxi, or ground operations.
99-03-08: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-600, -700, -700IGW, and -800 series airplanes. This action requires repetitive inspections to detect discrepancies of the quick-disconnect coupling on the fuel hose, located at the fan case firewall; corrective action, if necessary; and installation of a clamp shell on the coupling to prevent separation of the coupling halves. This amendment is prompted by a report that a quick-disconnect coupling on the fuel hose on an in-service airplane was found loose and leaking fuel. The actions specified in this AD are intended to detect and correct excessive wear of the quick-disconnect coupling on the fuel hose, which could result in major fuel leakage, fire in the engine nacelle, and consequent loss of thrust from the affected engine.
2021-20-01: The FAA is adopting a new airworthiness directive (AD) for all Pratt & Whitney PW1500G and PW1900G series turbofan engines with a certain high-pressure turbine (HPT) 1st-stage hub or HPT rotor 1st- stage blade retaining plate installed. This AD was prompted by a report from the manufacturer who determined that the HPT 1st-stage hub and HPT rotor 1st-stage blade retaining plate fail to meet the published life- cycle limits for each part. This AD requires removal and replacement of the HPT 1st-stage hub and HPT rotor 1st-stage blade retaining plate prior to reaching certain cycle limits. The FAA is issuing this AD to address the unsafe condition on these products.
68-12-05: 68-12-05 AERO COMMANDER: Amdt. 39-611. Applies to Models 100 and 100A, and Volaire Models 10A and 10, Serial Numbers 001 through 250. Compliance required as indicated. To preclude failure of the left and right arms, P/N 35321, of the rudder control system, accomplish the following: NOTE: The arms are those to which the rudder system left and right cables and springs are attached, and extend forward from the cross-bar assembly supporting the rudder pedals. (a) Within the next 10 hours' time in service after the effective date of this AD, unless already accomplished, inspect and modify the left and right arms, P/N 35321, as follows: Clean to bare metal all surfaces of the web and flanges of each arm over an area extending from the center of the 3/16 inch diameter cable attach hole to a point 3/4 inch aft of the hole. Visually inspect the exposed areas of the webs for cracks using a 10-power magnifying glass, or in an equivalent manner approved by the Chief,Engineering and Manufacturing Branch, FAA Southern Region. Weld the 1/16 inch deep square notches which are located in the webs at the forward ends of the upper and lower flanges of each arm, completely filling the notches with weld metal. Weld all cracks detected during the inspection with full penetration welds over the full length of each crack. Recoat the exposed area with oxide primer or equivalent. (b) Within the next 25 hours' time in service after the effective date of this AD, unless already accomplished, modify the left and right arms, P/N 35321, in accordance with the instructions contained in Aero Commander Service Bulletin 1009, dated May 24, 1968, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. This amendment becomes effective June 14, 1968.